Radiator for aeroplanes



May 28, 1929. H. c. MUMME RT RADIATOR FOR AEROPLANES 2 Sheets-Sheet Filed Aug. so, 1924 INVENTOR HARVEY CMUMME/PT- M y 8, 1929. H. c. MUMMERT 1,114,804

RADIATOR FOR AEROPLANES F iled Aug. 30, 1924 2 Sheets-Shet 2 v (I II" lugimllm PM 6 MENTOR,

" i ll HARVEY CMUNMEET l BY i m i 27 ATTORNEY HARVEY C. MUMMERT, OF HOLLIS, NEW YORK, ASSIGN'OR TO CURTISS AEROPLANE &

MOTOR 00., INC., OF GARDEN CITY, NEW YORK, A CORPORATION- OF NEW YORK.

RADIATOR FOR AEROPLAIVES.

Application filed August so, 1924. Serial no. 735,104.

My invention relates to radiators for aero.-'

planes and more particularly to improvee inents which are adapted to very appreciably reduce the air resistance of the radiator during the translation of the aeroplane thru the air.

In the drawings, wherein the preferred embodiment of the inveiition is illustrated:

" Fig. 1 is a side elevation of the radiator showingits relation to the aeroplane ofwhich the radiator fornisapart; I

Fig. end elevation, partly brolren away,fi irt her illustrating the radiator and ts associated cz sirngig;v v Fig. .5.is a fragmentary view illustrating in detail the radiator shutter operating mechanism; and,

'Fig. 6 is a View similar to the shutter operating inech'anism is viewed from a different-angle. r The aeroplane of which the radiator forms a part may be of any desired construction, or, if desired, the radiator may be used'on or in connection with other forms of self-propelled vehiclesthan the aeroplane. In the enibodiment of the invention selected for! illustration the Wings or supporting surfaces of the aeroplane are designated as 10, the fuselage or body as 11, the motor as 12, and the Wing struts as 13. The radiator and its associated structure, by means of Which its resistance is reduced, is designated as an entirety as 14. Preferably such structure is mounted in proximity to one of the supporting struts 13 Whereby it (the strut) provides the radiator suport.

The-radiator per known construction. As illustrated, it is 9f the honey-comb type in that it comprises a plurality of separated air and Water passages thru which the liquid cooling agent on the one hand and the air on .the other hand are adapted to pass to effect the desired interchange of heat. On either side of the radiator 15 Water passages 16 are provided. Such passages extend throughout the full length of the radiator and communicate at one end With a header 17, integral with the Figure 5. in which se may be of-any vvell' radiator, and preferably of streamline form. v l. he header 1] enters IHtOZ and forms an actual part oftlie streamlinecasingjlii within which,

the radiator 15 is enclosed.

sitely 'ci irved and suitablyjspaced sidewalls. 15y inountingthe rad ator in the mannerindr. cated, its resistance to duc-ed approximately er cent.

In addition to the vheadei lv'r'.atione enid ofv i the radiator a headerl19 is" provided at its forward travel is. re-'.

Said'casing '18.]v comprises in addition to theheaderfl'foppm opposite end, This header l9 in vieiv,o f ;the

, fact that it is entirely enclosed. in -the;. aero.

plane fuselageor body 11, andflregardless of:

The cooling agent, iiiit sfcirculatifon, is ivith-W, drawn fro 'irtl eglieader '15} means of a pipe motor 12' the cooling agent is pu'mpedto and thru the ater passages .16 on opposite sides,

of the radiator, and by g neansof the water passages is' conductedlto; thejheader 1'j(' a1id since the passages 16am forined,. in ,part'hYQ ,80. somewhat .lbefoie. lrea hing' the outer ejI ld i the casing sides, obviously. theagent cooled header. From the header 17 the cooling agent enters the radiator proper. The sidewalls of the casing 18 are preferably made sectional. The forward section, designated as 21, is hinged to the intermediate section, designated as 22, as indicated at 23, and the rear section designated as 24 is hingedto said intermediate section as indicated at 25. Thus connected and arranged, obviously the forward and rear sections 21 and 24 can, if neecssary,be adjusted. Between the rear sections 24: of the casing a shutter for the radiator is mounted. The shutter, in the embodiment of the invention selected for illustration, in one positi on of adjustment constitutes a barrier against the passage of air thru the casing 18 and in a different position of'adjustment provides fairing for that portion of the supporting strut 13 disposed between the casing sides. In Figure 3 the flaps 26 which serve on the one hand as a'radiator shutter and on the other hand as the strut fairing are best illustrated.

Preferably these flaps are fastened along one movable in the direction of the length of the flaps 26 to move the flaps about their respec dotted. line position indicated in. Fig. 3.

. v .When the flaps 26 arespread as indicated by the full lines of Fig. 3, an effective shutter for the radiator is provided. In this latter position'itis not necessary that the strut 13 b faired.

While I have described my invention in detail in its present preferred embodiment, it

will be obvious to those skilled in the art after understanding In invention, that various changes and modifications may be made there in without departing from thespirit or scope thereof.- I aim in-the appended claims to cover all such modifications and changes.

What I claim is: ,1. In combination, a self-propelled vehicle,

" -a casing comprising substantially parallel side walls appropriately spaced to provide I openings respectively at the forward end and at the rear end of the casing, a radiator mounted between the side walls of the casing and intermediately of said openings, a support for the radiator enclosed for a portion of its length-within said casing, and a shutter for the radiator carried by said support.

2. The combination with an aeroplane, of a radiator mounted in proximity to a structural element of aeroplane, and a shutter for said radiator comprising hinged fairing pieces fastened to said element, said fairing 40' pieces being relatively movable from a non-, shuttering position in engagement one with c the other to a shuttering position in which v said pieces are widely spaced.

3i In combination, a self-propelled vehicle including a supportlng element, a radiatormgunted in proximity to said element, a casing within which said radiator is enclosed and between the side walls of which said ele-' .ment extends, and a shutter for said radiator comprising hinged fairing pieces fastened to sa d element, said fairing pleces being rela- Lively movable from a non-shuttering position in which they fair said element to a shuttering position in which said pieces are 5 widely spaced to respectively engage, in their finally adjusted position, the opposite faces ofsaid casing wall.

4. In combination, a self-propelled vehicle,

an open end casing, a-radiator mounted within said casing intermedlately of its opposite open ends, an element of said Vehicle carried thru said casing behind'said radiator, and a shutter for said radiator comprising hinged fairing pieces fastened to said element, said fairing pieces being movable-from a nonshuttering position in "which they fairsaid element by engagement one with the other to a shuttering position in Which the opening at one end of said casing is completely closed by spreading said fairing pieces untilthey respecively engage the opposite inside faces of the casing Wall.

In testimony whereof I hereunto aflix my signature.

HARVEY c. 'MUMMERT. 

